Scientific and Technical Aerospace Reports Volume 39 April 6, 2001

20010026207 NASA, Washington, DC USA
Briefing Number 3 to Space Station Operations Task Force Oversight Committee
Lyman, Peter, NASA, USA; Shelley, Carl, NASA, USA; Jan. 28, 1987; 45p; In English; No Copyright; Avail: CASI; A03, Hardcopy;
A01, Microfiche
This document reviews certain issues in relationship to the operation of the Space Station Freedom. The document is in outline
format and includes some organizational hierarchy charts, pert charts and decision charts.
CASI
Space Station Freedom; Space Station Payloads; Space Station Structures; Mission Planning
20
SPACECRAFT PROPULSION AND POWER
Includes main propulsion systems and components, e.g., rocket engines; and spacecraft auxiliary power sources. For related information,
see also 07 Aircraft Propulsion and Power; 28 Propellants and Fuels; 15 Launch Vehicles and Launch Operations; and 44 Energy
Production and Conversion.
20010023936 NASA Langley Research Center, Hampton, VA USA
A Combined Experimental/Computational Investigation of a Rocket Based Combined Cycle Inlet
Smart, Michael K., Lockheed Martin Corp., USA; Trexler, Carl A., NASA Langley Research Center, USA; Goldman, Allen L.,
Boeing Co., USA; [2001]; 10p; In English; 39th; Aerospace Sciences, 8-11 Jan. 2001, Reno, NV, USA; Sponsored by American
Inst. of Aeronautics and Astronautics, USA
Report No.(s): AIAA Paper 2001-0671; Copyright Waived; Avail: CASI; A02, Hardcopy; A01, Microfiche
A rocket based combined cycle inlet geometry has undergone wind tunnel testing and computational analysis with Mach 4
flow at the inlet face. Performance parameters obtained from the wind tunnel tests were the mass capture, the maximum back-pressure,
and the self-starting characteristics of the inlet. The CFD analysis supplied a confirmation of the mass capture, the inlet efficiency
and the details of the flowfield structure. Physical parameters varied during the test program were cowl geometry, cowl
position, body-side bleed magnitude and ingested boundary layer thickness. An optimum configuration was determined for the
inlet as a result of this work.
Author
Rocket-Based Combined-Cycle Engines; Computational Fluid Dynamics; Flow Distribution; Wind Tunnel Tests
20010024038 Applied Research Associates, Inc., Littleton, CO USA
Development of a Predictive Model for Rocket Launch Noise Footprint Final Report
White, Michael J., Applied Research Associates, Inc., USA; Nov. 27, 2000; 56p; In English
Contract(s)/Grant(s): F41624-99-C-6033
Report No.(s): AD-A384661; AFRL-HE-WP-0001AD; No Copyright; Avail: CASI; A01, Microfiche; A04, Hardcopy
During rocket launch significant noise can be generated and propagated to the surrounding environment that can be disrupting
to both communities and wildlife. Assessment of these impacts requires knowledge of the acoustic source mechanisms, propagation
effects, and requirements under the National Environmental Policy Act. In Phase I we will draw heavily on the rocket engine
acoustic source investigative testing that we recently completed as well as expand our recent literature source on rocket engine
acoustic sources. Our far field acoustic propagation techniques, developed from explosive charge detonation and large calibre gun
firing tests, will be combined with our knowledge of rocket (engine noise and vehicle bow shock) sources to form a preliminary
far field noise footprint prediction method. It is anticipated the results would be shown graphically using Air Force developed
software, NMPLOT. Also, we intend to add IBON to our current noise criteria database. In Phase II the noise footprint software
will be formalized, tested with field measurements and graphical user interface will be added to complete the noise assessment
tool.
DTIC
Noise Pollution; Computer Programs; Noise Reduction; Rocket Launching; Acoustic Propagation; Bow Waves; Noise Prediction;
Prediction Analysis Techniques; Rocket Engine Noise
19